XFOIL Version 6.96 Calculated polar for: FX 73-CL3-152 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 0.1961 0.09443 0.09149 -0.1272 0.8896 0.0349 -10.000 0.2050 0.09216 0.08920 -0.1281 0.8814 0.0359 -9.750 0.1892 0.08787 0.08489 -0.1328 0.8735 0.0374 -9.500 0.2068 0.08560 0.08258 -0.1324 0.8663 0.0377 -9.250 0.2194 0.08386 0.08084 -0.1317 0.8568 0.0379 -9.000 0.2329 0.08218 0.07912 -0.1317 0.8477 0.0383 -8.750 0.2416 0.08044 0.07737 -0.1315 0.8370 0.0387 -8.500 0.2501 0.07863 0.07552 -0.1315 0.8252 0.0397 -8.250 0.2310 0.07430 0.07117 -0.1353 0.8138 0.0421 -8.000 0.2383 0.07197 0.06882 -0.1345 0.7968 0.0424 -7.750 0.2478 0.07056 0.06732 -0.1333 0.7696 0.0426 -7.500 0.2535 0.06962 0.06612 -0.1308 0.7133 0.0429 -7.250 0.2569 0.06873 0.06494 -0.1285 0.6650 0.0433 -7.000 0.2609 0.06747 0.06352 -0.1273 0.6330 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0.00639 -0.1681 0.4122 0.4682 3.500 1.2073 0.01366 0.00657 -0.1675 0.4101 0.5074 3.750 1.2320 0.01376 0.00675 -0.1668 0.4081 0.5492 4.000 1.2564 0.01386 0.00692 -0.1661 0.4060 0.5922 4.250 1.2806 0.01397 0.00711 -0.1654 0.4039 0.6371 4.500 1.3052 0.01413 0.00733 -0.1647 0.4015 0.6859 4.750 1.3319 0.01432 0.00761 -0.1646 0.3986 0.7530 5.000 1.3883 0.01429 0.00787 -0.1708 0.3966 1.0000 5.250 1.4134 0.01446 0.00804 -0.1704 0.3948 1.0000 5.500 1.4385 0.01465 0.00822 -0.1699 0.3927 1.0000 5.750 1.4635 0.01484 0.00841 -0.1694 0.3906 1.0000 6.000 1.4883 0.01505 0.00860 -0.1689 0.3885 1.0000 6.250 1.5129 0.01527 0.00880 -0.1684 0.3864 1.0000 6.500 1.5380 0.01554 0.00903 -0.1680 0.3842 1.0000 6.750 1.5661 0.01597 0.00939 -0.1682 0.3812 1.0000 7.000 1.5882 0.01614 0.00962 -0.1673 0.3797 1.0000 7.250 1.6096 0.01633 0.00984 -0.1662 0.3776 1.0000 7.500 1.6308 0.01654 0.01009 -0.1651 0.3753 1.0000 7.750 1.6523 0.01676 0.01033 -0.1641 0.3730 1.0000 8.000 1.6738 0.01700 0.01057 -0.1631 0.3708 1.0000 8.250 1.6955 0.01726 0.01084 -0.1621 0.3686 1.0000 8.500 1.7186 0.01760 0.01114 -0.1615 0.3662 1.0000 8.750 1.7437 0.01800 0.01153 -0.1613 0.3636 1.0000 9.000 1.7619 0.01826 0.01187 -0.1599 0.3618 1.0000 9.250 1.7806 0.01855 0.01222 -0.1585 0.3594 1.0000 9.500 1.7998 0.01886 0.01258 -0.1574 0.3569 1.0000 9.750 1.8190 0.01918 0.01293 -0.1562 0.3544 1.0000 10.000 1.8383 0.01953 0.01330 -0.1551 0.3520 1.0000 10.250 1.8588 0.01994 0.01369 -0.1543 0.3496 1.0000 10.500 1.8806 0.02040 0.01415 -0.1536 0.3469 1.0000 10.750 1.8967 0.02084 0.01469 -0.1522 0.3448 1.0000 11.000 1.9133 0.02129 0.01523 -0.1509 0.3423 1.0000 11.250 1.9300 0.02177 0.01576 -0.1496 0.3397 1.0000 11.500 1.9463 0.02226 0.01629 -0.1483 0.3370 1.0000 11.750 1.9632 0.02279 0.01683 -0.1471 0.3344 1.0000 12.000 1.9806 0.02338 0.01740 -0.1460 0.3310 1.0000 12.250 1.9911 0.02409 0.01824 -0.1442 0.3277 1.0000 12.500 2.0024 0.02482 0.01905 -0.1425 0.3236 1.0000 12.750 2.0140 0.02560 0.01985 -0.1409 0.3197 1.0000 13.000 2.0272 0.02641 0.02062 -0.1395 0.3159 1.0000 13.250 2.0381 0.02732 0.02166 -0.1380 0.3129 1.0000 13.500 2.0498 0.02822 0.02266 -0.1366 0.3096 1.0000 13.750 2.0609 0.02919 0.02369 -0.1352 0.3065 1.0000 14.000 2.0710 0.03024 0.02476 -0.1337 0.3035 1.0000 14.250 2.0804 0.03136 0.02589 -0.1322 0.3000 1.0000 14.500 2.0892 0.03258 0.02724 -0.1308 0.2972 1.0000 14.750 2.0975 0.03386 0.02862 -0.1294 0.2939 1.0000 15.000 2.1043 0.03527 0.03008 -0.1279 0.2903 1.0000 15.250 2.1083 0.03692 0.03173 -0.1263 0.2865 1.0000 15.500 2.1127 0.03868 0.03360 -0.1250 0.2826 1.0000 15.750 2.1160 0.04061 0.03563 -0.1238 0.2781 1.0000 16.000 2.1164 0.04284 0.03789 -0.1225 0.2736 1.0000 16.250 2.1160 0.04520 0.04030 -0.1212 0.2695 1.0000 16.500 2.1172 0.04759 0.04282 -0.1203 0.2655 1.0000 16.750 2.1147 0.05036 0.04566 -0.1193 0.2610 1.0000 17.000 2.1082 0.05357 0.04887 -0.1183 0.2565 1.0000 17.250 2.1054 0.05656 0.05201 -0.1176 0.2526 1.0000 17.500 2.0981 0.06008 0.05563 -0.1170 0.2477 1.0000 17.750 2.0858 0.06418 0.05974 -0.1163 0.2428 1.0000 18.000 2.0752 0.06824 0.06392 -0.1159 0.2378 1.0000 18.250 2.0604 0.07285 0.06862 -0.1156 0.2321 1.0000 18.500 2.0411 0.07797 0.07376 -0.1153 0.2264 1.0000 18.750 2.0232 0.08315 0.07908 -0.1153 0.2200 1.0000 19.000 1.9996 0.08901 0.08495 -0.1153 0.2135 1.0000 19.250 1.9788 0.09464 0.09069 -0.1156 0.2061 1.0000